EP2276911A1 - Turbomaschinenrotor mit einem verschleissfesten stopfen und verschleissfester stopfen - Google Patents

Turbomaschinenrotor mit einem verschleissfesten stopfen und verschleissfester stopfen

Info

Publication number
EP2276911A1
EP2276911A1 EP09731437A EP09731437A EP2276911A1 EP 2276911 A1 EP2276911 A1 EP 2276911A1 EP 09731437 A EP09731437 A EP 09731437A EP 09731437 A EP09731437 A EP 09731437A EP 2276911 A1 EP2276911 A1 EP 2276911A1
Authority
EP
European Patent Office
Prior art keywords
plug
cap
ring
fastener
turbomachine rotor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP09731437A
Other languages
English (en)
French (fr)
Other versions
EP2276911B1 (de
Inventor
Thomas Chrzastek
Jean-Bernard Forgue
Dominique Gaveau
Patrick Jean-Louis Reghezza
Nicolas Christian Triconnet
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Mersen France Gennevilliers SAS
Original Assignee
Carbone Lorraine Composants
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Carbone Lorraine Composants, SNECMA SAS filed Critical Carbone Lorraine Composants
Publication of EP2276911A1 publication Critical patent/EP2276911A1/de
Application granted granted Critical
Publication of EP2276911B1 publication Critical patent/EP2276911B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to the field of gas turbine engines and aims in particular a turbofan engine before.
  • the turbofan rotor of an engine fitted to civil aircraft includes a disk driven by the low pressure shaft.
  • a plurality of blades extends radially to the periphery of the disc, and the blades are retained by their end which forms the foot.
  • the blade root is dovetailed section and these are housed in cavities machined in the rim of the disk in an axial direction.
  • the booster compressor Immediately downstream of the fan disk and forming the same rotor is the booster compressor. It is drum-shaped and includes several blade stages.
  • the fan disk is secured to the drum of the booster compressor by bolting to a radial flange of the latter.
  • the flange is also provided with notches forming an axial retention means of the vanes of the fan disk.
  • Each blade root is provided downstream of an axial extension with two radial grooves and is engaged in a notch at the grooves so as to be blocked against axial displacement.
  • a turbomachine rotor comprising a disk with a rim and axial cavities machined on the rim for the individual housing of blades, a ring being attached to one face of the rim, ring being pierced with holes in the axial extension of the cells, at least a portion of said holes in the extension of the cells comprising a plug, characterized in that the plug is formed of a first half plug made of a first material resistant to wear and a second half plug in a second material, the two half plugs bearing one on one side of the ring and the other on the other side of the ring and connected one to another through the hole.
  • the stopper also maintains the seal with the downstream cavity.
  • the first half cap comprises a disc-shaped portion with flange and a fastener
  • the second half-cap a disc-shaped portion with flange and a fastener
  • the two fasteners being of complementary shapes to cooperate with each other. with each other.
  • the fasteners may be, for example, screw or in the form of a clip, the attachment of the first half cap being male and the attachment of the second female half cap.
  • the stopper is preferably arranged so as not to injure the metal constituting the drum. Indeed, it is a question of interventions by a technician to avoid the formation of any start of creek.
  • This means is formed of markings allowing the establishment of a tool ensuring the attachment, for example by screwing and unscrewing the first half cap or by clipping.
  • first half cap is made of metal, for example steel, and the second half cap is plastic. Other materials are possible. They can be identical or not.
  • the invention also relates to a plug arranged to form an anti-wear device.
  • the invention also relates to a gas turbine engine compressor rotor, comprising a rotor disc with a rim secured to a ring, the disc rim having axial recesses for the housing of blades, the ring covering at least partially the downstream edge of the cells and having stress relief bores of which a portion is disposed in the axial extension of said cells, and comprising a plug as described above.
  • the turbomachine rotor disk is a fan disk in a front fan turbojet engine attached to a low pressure compressor drum.
  • the ring is secured to the compressor drum and the rotor disk is fixed to the drum by bolting to the ring.
  • the holes are stress relief holes.
  • the invention applies primarily to a turbojet comprising a front fan and a booster compressor downstream of the fan, the fan disk and the compressor drum form the rotor of the invention.
  • FIG. 1 shows a side view of a turbojet engine to which the anti-wear device of the invention applies
  • FIG. 2 shows in perspective the detail of a turbojet fan rotor on the side of the upstream flange of the booster compressor
  • Figure 3 shows the detail of the flange shown in Figure 2 with an anti-wear device
  • Figure 4 shows in axial section through a hole the arrangement of the plug according to the invention
  • Figure 5 shows the head of the half plug located on the side of the cells
  • FIG. 1 shows a turbojet engine 1, in axial section. It comprises a front blower 2 with a shrouded rotor in a fan casing 3 which delimits the secondary flow vein.
  • the rotor 2 of the blower is secured to a low-pressure compressor 4, again referred to as a booster compressor.
  • the assembly of the fan 2 and the booster compressor is secured, by means of a central shaft, of a set of turbines forming the low-pressure turbine 8.
  • the air Downstream of the booster compressor 4 the air is still compressed by the high-pressure compressor 5.
  • the latter is rotatably connected to the high-pressure turbine stage 7 by which it is driven.
  • the compressed air enters the combustion chamber 6 which produces the hot gases to drive the turbine stages.
  • the invention concerns the portion of the motor disposed between the fan rotor 2 and the rotor 4 of the low-pressure compressor.
  • FIG. 2 shows, in perspective, the interior of this zone in which the fan blades have been omitted.
  • the fan disk 20 comprises, on its rim, cells 21 oriented generally axially with here a curvilinear shape.
  • the cells are section dovetail.
  • the rim comprises radial flanges 22 between the cells for fixing inter-blade platforms.
  • the disc 20 is integral with the low pressure compressor 4 located downstream.
  • the compressor comprises a cylindrical drum 41 on which are fixed the compressor blades 42 that can be seen in part. Upstream, the drum is secured to a radial flange 43 on which the rim of the disc 20 is bolted.
  • the rim comprises radial attachment flanges 23 between the cells 21. Each radial flange 23 is fixed by a bolt 24 to the upstream flange 43 of the compressor.
  • the upstream flange 43 has retention slots 43a with radial edges and which are open towards the axis of the machine. These notches are used to retain the blades axially by introducing the foot of the blade vis-à-vis. This blade retention method is described in the patent in the name of the Applicant EP 165860. Between the fastening flanges 23, on a circle of the same diameter, holes 44 are formed on the upstream flange 43. The function of these holes is to relax the stresses to which this piece is subjected. Sealing plugs prevent the air downstream, inside the drum 41, from leaking upstream whose pressure is lower. These sealing plugs are made of synthetic material and do not perform any other function.
  • the motor can be autorotated with reversal of forces on the blades.
  • the vanes bear against the flange 43 by the downstream face of their stilt.
  • the pressure and displacements of the vanes cause wear of both the blade and the upstream flange.
  • the trace T of wear left by Péchasse dawn on the flange This trace is located in the extension of the cells and overlaps a bore 44. This results in uneven wear of the Péchasse with digging of the material around the area which is in the axis of the bore.
  • Figure 3 shows the same engine area as Figure 2, also without the blades. Only a portion of the fan disk 20 is shown. It is associated with the upstream flange 43 of the downstream low pressure compressor. The bore 44 which is opposite the cell 21, in its extension, is closed by a plug 50. This plug is arranged to form a bearing surface for the blade which is in this cavity but which is not shown in the figure.
  • the stopper 50 comprises two half-plugs 51 and 52. One on each side of the bore 44.
  • the half cap 51 on the blade side A has a head
  • the half-cap 51 comprises a fastener 51b ensuring the connection with the half-plug 52.
  • the half-plug 51 is made of a material which is resistant to corrosion. wear, for example of metal.
  • the head 51a also has three marks 51c for introducing a tool by which the half stopper can be attached to the stem, for example by screwing but other means are also possible.
  • the half-cap 52 which is made of a plastics material, comprises a head 52a bearing against the opposite face of the upstream flange 43.
  • the head 52a is also disk-shaped with a flange.
  • the half plug is extended in the bore 44 by a fastener 52b which cooperates with the fastener 51b of the half-cap 51 to form a connection and hold the two half plugs tight to each other on either side of the upstream flange 43.
  • the fastener 51b is in the form of a threaded rod cooperating by screwing with the female fastener 52b.
  • FIG. 6 which is a front view of the half-cap 52, the head 52a has an edge 52a 'forming anti-rotation means while bearing against a recess 43' machined on the upstream flange 43.
  • the cap assembly is as follows.
  • the half-plug 52 In an initial phase during a motor assembly, the half-plug 52 is placed in the bore through the inside of the drum.
  • the outer diameter of the female fastener 52b allows a force fit of the half-plug 52 by introducing the female fastener 52b into the bore 44.
  • the half-cap 51 is then placed on the other side and fixed with a three-spoke tool in the marks 51c of the head 51a.
  • the head 51a forms a bearing surface, sufficient for the efforts to be distributed.
  • the resistance of the head 51a is also sufficient so that the metal does not enter the bore.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09731437A 2008-04-07 2009-04-07 Turbomaschinenrotor mit einem verschleissfesten stopfen und verschleissfester stopfen Active EP2276911B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0801901A FR2929660B1 (fr) 2008-04-07 2008-04-07 Dispositif anti-usure pour rotor de turbomachine, bouchon formant dispositif anti-usure et rotor de compresseur de moteur a turbine a gaz comportant un bouchon anti-usure
PCT/EP2009/054174 WO2009124949A1 (fr) 2008-04-07 2009-04-07 Rotor de turbomachine comportant un bouchon anti-usure, bouchon anti-usure

Publications (2)

Publication Number Publication Date
EP2276911A1 true EP2276911A1 (de) 2011-01-26
EP2276911B1 EP2276911B1 (de) 2011-09-28

Family

ID=39929685

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09731437A Active EP2276911B1 (de) 2008-04-07 2009-04-07 Turbomaschinenrotor mit einem verschleissfesten stopfen und verschleissfester stopfen

Country Status (11)

Country Link
US (1) US8985961B2 (de)
EP (1) EP2276911B1 (de)
JP (1) JP5608634B2 (de)
CN (1) CN102046923B (de)
AT (1) ATE526487T1 (de)
BR (1) BRPI0911190B1 (de)
CA (1) CA2720807C (de)
ES (1) ES2373363T3 (de)
FR (1) FR2929660B1 (de)
RU (1) RU2496988C2 (de)
WO (1) WO2009124949A1 (de)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2955904B1 (fr) * 2010-02-04 2012-07-20 Snecma Soufflante de turbomachine
FR2964584B1 (fr) * 2010-09-10 2013-08-16 Snecma Dispositif et procede de frettage d'une piece anti-usure dans un trou localise dans un element de turboreacteur
FR2968363B1 (fr) * 2010-12-03 2014-12-05 Snecma Rotor de turbomachine avec une cale anti-usure entre un disque et un anneau
US8864446B2 (en) * 2011-05-23 2014-10-21 Siemens Energy, Inc. Wear pin gap closure detection system for gas turbine engine
US8622016B2 (en) * 2011-10-04 2014-01-07 Siemens Energy, Inc. Wear indication system for compressor diaphragms of gas turbine engines
FR2986284B1 (fr) 2012-01-31 2014-03-28 Snecma Procede de reparation de marques d’usure.
WO2014197074A2 (en) * 2013-03-14 2014-12-11 United Technologies Corporation Curvic seal for gas turbine enigne
EP2933436A1 (de) * 2014-04-15 2015-10-21 Siemens Aktiengesellschaft Radscheibe mit wenigstens einem Dichtblech
US10047763B2 (en) 2015-12-14 2018-08-14 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
FR3048448B1 (fr) * 2016-03-02 2018-03-30 Safran Aircraft Engines Bouchon d'etancheite pour tambour de compresseur basse pression, tambour de compresseur basse pression et turbomachine associes
US11428104B2 (en) 2019-07-29 2022-08-30 Pratt & Whitney Canada Corp. Partition arrangement for gas turbine engine and method

Family Cites Families (11)

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Publication number Priority date Publication date Assignee Title
FR2502690B1 (fr) * 1981-03-27 1985-09-13 Snecma Dispositif de verrouillage d'aubes de soufflante et de fixation de capot avant d'un turboreacteur
US4483661A (en) * 1983-05-02 1984-11-20 General Electric Company Blade assembly for a turbomachine
US4523890A (en) * 1983-10-19 1985-06-18 General Motors Corporation End seal for turbine blade base
FR2566061B1 (fr) 1984-06-14 1988-09-02 Snecma Dispositif de verrouillage axial d'une aube de turbomachine
US5259728A (en) * 1992-05-08 1993-11-09 General Electric Company Bladed disk assembly
US6520742B1 (en) * 2000-11-27 2003-02-18 General Electric Company Circular arc multi-bore fan disk
FR2819289B1 (fr) * 2001-01-11 2003-07-11 Snecma Moteurs Systeme de retention des aubes de type combine ou cascade
US6857854B2 (en) * 2002-07-12 2005-02-22 Hunter Fan Company Quick connect blade system
FR2844562B1 (fr) * 2002-09-18 2004-10-29 Snecma Moteurs Maitrise de la position axiale d'une aube de rotor de soufflante
FR2903154B1 (fr) * 2006-06-29 2011-10-28 Snecma Rotor de turbomachine et turbomachine comportant un tel rotor
FR2905139B1 (fr) * 2006-08-25 2012-09-28 Snecma Aube de rotor d'une turbomachine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009124949A1 *

Also Published As

Publication number Publication date
JP2011516785A (ja) 2011-05-26
US8985961B2 (en) 2015-03-24
EP2276911B1 (de) 2011-09-28
RU2496988C2 (ru) 2013-10-27
WO2009124949A1 (fr) 2009-10-15
CN102046923A (zh) 2011-05-04
ATE526487T1 (de) 2011-10-15
CA2720807A1 (fr) 2009-10-15
RU2010145155A (ru) 2012-05-20
BRPI0911190A2 (pt) 2015-10-13
FR2929660B1 (fr) 2012-11-16
BRPI0911190B1 (pt) 2019-12-03
CN102046923B (zh) 2013-12-11
US20110033283A1 (en) 2011-02-10
JP5608634B2 (ja) 2014-10-15
ES2373363T3 (es) 2012-02-02
FR2929660A1 (fr) 2009-10-09
CA2720807C (fr) 2016-06-14

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